scholarly journals High temperature fatigue testing of gas turbine blades

2017 ◽  
Vol 7 ◽  
pp. 206-213 ◽  
Author(s):  
M. Beghini ◽  
L. Bertini ◽  
C. Santus ◽  
B.D. Monelli ◽  
E. Scrinzi ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fatigue Testing ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Fatigue

UDIMET L-605

Alloy Digest ◽  
2004 ◽  
Vol 53 (12) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
Gas Turbine ◽  
Oxidation Resistance ◽  
Turbine Blades ◽  
Heat Treating ◽  
Gas Turbine Blades ◽  
Temperature Performance

Abstract Udimet L-605 is a high-temperature aerospace alloy with excellent strength and oxidation resistance. It is used in applications such as gas turbine blades and combustion area parts. This datasheet provides information on composition, physical properties, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, and joining. Filing Code: CO-109. Producer or source: Special Metals Corporation.

High Temperature Degradation of Coating and Substrate in Gas Turbine Blade

1995 ◽  
Author(s):  
Y. Sugita ◽  
M. Ito ◽  
N. Isobe ◽  
S. Sakurai ◽  
C. R. Gold ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Cross Sections ◽  
Turbine Blades ◽  
Temperature Oxidation ◽  
Gas Turbine Blades ◽  
Coating Surface ◽  
Ductile Brittle Transition Temperature ◽  
Scanning Auger Microprobe ◽  
Long Time

This paper studied high temperature degradation behavior of gas turbine blades consisting of CoNiCrAlY coatings and Rene 80 substrates using a small punch (SP) testing technique at 295–1223 K and scanning Auger microprobe (SAM). In SP tests, coating cracks continuously propagated along the radial direction at 295 K and many cracks discretely were formed along more random directions at higher temperatures. The ductility of the coating at 295 K was reduced and the ductile-brittle transition temperature was increased during long time exposure of gas turbine blades to high temperature oxidation environments. SAM analyses on cross sections and fracture surfaces of the coatings indicated that oxidation and S segregation near the coating surface are profoundly induced in-service. The relationship between the mechanical properties and microstructural/chemical evolution near the coating surface is presented which serves as a data base for determining the remaining life of gas turbine blades.

De-alloying and fatigue of high temperature alloys used for gas turbine blades

1995 ◽  
Vol 13 (2) ◽  
pp. 81-86 ◽  
Author(s):  
L. B. Getsov ◽  
A. I. Rybnikov ◽  
P. G. Krukovski ◽  
E. C. Kartavova
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Alloys

scholarly journals A Novel Method for High Temperature Fatigue Testing of Nickel Superalloy Turbine Blades with Additional NDT Diagnostics

Materials ◽  
2021 ◽  
Vol 14 (6) ◽  
pp. 1392
Author(s):  
Dominik Kukla ◽  
Mateusz Kopec ◽  
Ryszard Sitek ◽  
Aleksander Olejnik ◽  
Stanisław Kachel ◽  
...  
Keyword(s):  
Finite Element ◽  
High Temperature ◽  
Fatigue Testing ◽  
Turbine Blades ◽  
Nickel Superalloy ◽  
Fe Model ◽  
Destructive Testing ◽  
High Temperature Fatigue ◽  
Bending Load ◽  
Novel Method

In this paper, a novel method for high temperature fatigue strength assessment of nickel superalloy turbine blades after operation at different times (303 and 473 h) was presented. The studies included destructive testing (fatigue testing at temperature 950 °C under cyclic bending load), non-destructive testing (Fluorescent Penetrant Inspection and Eddy Current method), and finite element modelling. High temperature fatigue tests were performed within load range from 5200 to 6600 N using a special self-designed blade grip attached to the conventional testing machine. The experimental results were compared with the finite element model generated from the ANSYS software. It was found that failure of turbine blades occurred in the area with the highest stress concertation, which was accurately predicted by the finite element (FE) model.

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